Aircraft



B. B. SMITH June 4,

AIRCRAFT Original File d Sept. 26, 1933 2 Sheets-Sheet 1 Snnentor fieau/ol/B, 5117i! 7 Gnomeg June 1940- B. B. SMITH Re. 21,478

AIRCRAFT Original Filed Sept. 26, 1933 2 Sheets-Sheet 2 Snventor I Gitorncg 6 pilot of the Reali es it... 4, 1640 PATENT orrlcs AIRCRAFT vBeituford B. Smith, San Diego,

Edward F. Andre Original No. 2,008,848, dated rial No. 690,979, September-26, 19$.

Calif., assignor to Chicago, Ill

July 23, 1935, 8e- Applica- 'tion for reissue July 16, 1937, Serial No. 158,950

16 Claims.

This invention relates to improvements in aircraft'and more especially to the autogyro type of aircraft wherein a plurality of rotating airfoils are used to create lifting power for vertical and 5 forward flight of the aircraft. 7

One of the principal objects of the invention is to provide a mechanism of this character whereby the craft will have a high flyin Speed and a low landing speed.

. Another object of the invention is the provision this character wherein the said airfoils are mounted to a-common drive shaft to which they are partially independently of a gyro mechanism of rotatably mounted and whereby the shaft engages the blades progressively one after another and automatically arranges them in-equi-distant angular relationship to' each other and also whereby said airfoils will automatically release themselves for automatically positioning into a' N positionof rest. v

Another object of the invention is to provide a means whereby said airfoils are collapsible to a position of rest'wherein they are arranged one upon the other and in such position adapted to ll be housed within the streamline confines of the aircraft body, thereby oil'ering no parasite resistance. whatever to the forward flight aircraft. a

Another objectof the invention is the provi- W sion of automatic means for projecting the airfoils from a position of rest within the fuselage of the aircraft to an operative position above the aircraft. By this same means the airfoils may be readily retracted into an inoperative position and I! housed within the fuselage. In other words, for

the take-off of the aircraft, to which my invention is applied, it is merely newssary for the pilot to operate a control within the cockpit of the ship for releasing the airfoils into operative posi- 0) tion, whereupon they are caused to rotate by a mechanical means hereinafter described, to create maximum lifting power for causing a rapid ascension of the aircraft. I

Upon reaching. a predetermined altitude the aircraft may then retract the alrioils v as aforesaid within the fuselage of the ship and then the relatively small wings of the aircraft are alone used for straightaway flight. By this arrangement it is obvious that,-due to the small 50 wing area, my improved type of aircraft is capable of a high rate of flying speed and a low rate of descent or landing speed.

vention is more fully hereinafter described in the following specification, illustrated in- -the accomof thepanying drawings and flnally pointed out in the appended claims.

In the drawings Fig. 1 is a top plan view of my improved type'of aircraft showing my new and improved autogyro s mechanism in operative engag ment therewith.

Fig. 2 is a top plan view of an aircraft showing the airfolls of my autogyro collapsed andhoused within the fuselage of the aircraft.

Fig. 3 is a view similar to Figuresl and 2 and 10 V showing the airfoils in the process of assuming their inoperative positions for subsequent hour ing within the fuselage of the aircraft.

Fig. 4 is an enlarged fragmentary sectional side elevation of Figure 1. taken on line H of 15 Figure l, and with parts broken away for convenience of illustration.

Fig. 5 is an enlarged fragmentary sectional view, taken on the line 5-4 of Figure 2.

Fig. 6 is an enlarged detailed view of the ing mechanism for the airfoils themselves in inoperative position.

Fig. 7 is an enlarged detailed view of a pneumatic means for projecting and retracting said airfoils' with respect to the fuselage of the air- 2. craft.

Fig.8 is an enlarged fragmentary sectional plan view. taken on-the line H of Figure 6.

Fig. 9 is a similar view takenon thelineJ-J ofFigureGQ 0 Fig. 10 is an enlarged fragmentary plan view;

' taken on the line Ill-Ill of Figure 4.

Referring now more particularly to the Reference numeral I indicates the main body 35 drawor fuselage of an aircraft having 'wings I extending outwardly from theside thereof in the usualmanner. 3 and 4 indicate bearings securely mounted within the fuselage to rotatably support a hollow shaft 5-. The shaft 5 is longitudinally bored as at 6 and provided at its uppermost end with a felt or leather piston I or any other approved form of piston. Surrounding the shaft 5 and slidably mounted thereon is a tubular hous ing 8 which extends upwardly beyond the bearing 4. The uppermost end of the housing 8 is provided with a cap 9 which contains a lubricating oil reservoir packedwith felt or the like,.which renders the same air-tight between the top or the shaft 5 and its inner and uppermost end. The

housing 8 is rotatable with the shaft 5 through j the medium of' any suitable key mechanismbut- These and other objects will appear as my inthe housing is slidable vertically with respect to the shaft s by reason of an elongated key-way to permit of moving the housing 8 longitudinally- 5 driv- 20' around its pivot point Ii.

'I'he lowermost end of the longitudinally bored shaft I is connectedby any suitable means to -a pressure line it through which suitable pressure or suction may be directed shaft 5 and into the upper end of I for projecting or retracting the same with respect to said shaft 5. Upon the upper'end of the housing I, I secure an airfoil II by any suitable means such for instance as a pin it whereby said airfoil is rotatable with said housing at all times; Above and below said anchored air: foil, I provide companion airfoils i9 and 20 through the .which are rotatably mounted to the shaft through a predetermined degree of rotation but are provided withlimit stops 2| for abutment with corresponding limit'stops 22 formed on the central and anchoredairfoil so that as said central airfoil rotates with the shaft in one direction, it will progressively'pick up the companion airfoils l9 and 20 and likewise'upon rotation in the opposite direction it will progressively release said airfoils so that they may be swung by the slipstream or air incidental of flight around and over the body of the aircraft. Within the upper wall oi'the fuselage of the aircraft I provide a cavity 23 to form a housing, as aforesaid, and the. airfoils when they are in a positlon of rest are arranged one upon the other. .The uppermost end of the cavity is provided with any suitable closure plate 14 shaped to correspond with the contour of the aircraft body and hinged thereto along one of its edges by any suitable means.. For convenience in opening and closing said closure plate I provide a link 25 connected at one of its ends to the underside of the closure plate 24 and at its opposite end to a crank arm 2' to'which is secured an actuating rod 21 which extends to a point within convenient reach of the pilot' of the aircraft so that manipulation of the rod 21 will cause the closure plate to rapidly open to permit emergence of said airfoils. This closure controlling mechanism, as aforesaid, is not suiiiciently strong to overcome the projecting of the airfoils through the closure in the case of a forced landing or'the like, where, sudden application of pressure applied to the housing 8 will instantly project said housing and said airfoils up through the top of the cavity and in so doing swing the closure open against any resistance by the said controlling mechanism. As a modified form of closure fastening means I may provide a catch controllable from the cockpit and which may beswung out of locking engagement with the closure. I have not here shown this modified form of fastening" means since I am aware that any approved form of such fastening means may be employed.

In connection with the bevel gear ill, it is to be noted that the gear is slidably mounted upon the shaft 5 by means of a key IA, and operable with respect to the pinion II by means of the bell crank l3, as aforesaid.

Upon the bearing support 3 I form an upupper end with a brake shoe '33 arranged in the housing the path of downward movement of the bevel gear ll, so that a prolonged pull on the rod I4 and bell crank it will cause the gear to wipe against the brake shoe to effect a braking action thereupon.

While I have shown a particular form of embodiment of my invention I am aware that many minor changes therein will readily suggest themselves to those skilled in the art without departing from the spirit and scope of the invention.

Having thus described the invention, what I claim as new and desire to protect by Letters Patent is:

1. An aircraft of the class described, compris ing a fuselage, wings, an empennage and a power plant, a vertical shaft rotatably mounted within the fuselage and engageable with the power plant, a housing slidably mounted upon said shaft and rotatable therewith, said housing adapted to be projected from the interior of the fuselage to the exterior thereof, a plurality of airfoils mounted upon the housing and adapted to be projected or retracted with said housing from the interior of the fuselage to the exterior thereof, one of said airfoils being secured to the housing and the others being rotatably mounted upon the housing and means formed on said other of saidairfoils for becoming progressively engaged with the said secured airfoil.

2. An aircraft as in claim 1 including a cavity formed in the fuselage for receiving said airfoils when in retracted position.

3. In an aircraft having a fuselage, wings and an empennage, the combination of a plurality of individual radially directed airfoils mounted upon a drive shaft, means operable by the rotation of said shaft for arranging said airfoils in substantially equally spaced position, and means for retracting said airfoils in their rearward collapsed position to a position of rest within the fuselage in the direction of its length. r 4. In an aircraft having a fuselage, wings and an empennage, the combination of a vertically disposed power driven shaft, a housing slidably and rotatably mounted upon said shaft and adapted to be driven thereby, means for proiecting said housing above said fuselage and for retracting the housing to a position within the fuselage, an airfoil secured at one of its ends to said housing, a plurality of companion airfoils partially rotatably mounted upon said housing, cooperative limit stops formed on said first memtioned airfoil and on the companion airfoils for abutment with each other upon rotation of said radial airfoils mounted thereon, means connecting said member to the motor means, clutch means whereby the pilot may drive said member, brake means for said member, means carried by said member and operative when the member is driven for substantially equally spacing said air-' foils, said'airfoils being free to be moved rearwardly by the airstream into.substantially parallel relation when said clutch means are disconnected by the pilot during flight. 6. In an aircraft having a fuselage, moto means driving a horizontal propeller, a fixed wing system -comprising a rotatable member and a when driven by said propeller, a rotating wins plurality of independently movable generally radial airfoils mounted thereon, disengageable 'means connecting said member to the motor means whereby the'pilot may drive said member, means carried by said member and operative when the member is driven for substantially equally spacing said airfoils, said airfoils bein free to be moved rearwardly by the airstream; into substantially parallel relation when said 'disenm'eable means is disengaged, by the pilot during flight, means-for projecting and retracting said member with said airfoils in rearward parallel position during flight, and means for opening andclosing the top surface of said fuselage to permit the passage of said airfoil's therethrough.

I. An aircraft having a fuselage, a motor, stationary wings adapted to support the aircraft during high speed flight, a system of rotating wings mounted on the forward portion'of the fuselage comprising a telescopic shaft and a pinrality I of independent generally radial airfoils mounted on the upper end of said. shaft, means connecting said shaft to said motor whereby the. wing system may be rotated, means carried by said shaft for spacing said airfoils when theshaft is driven, means .for freeing said airfoils to cause them to be moved rearwardly by the airstream to a position substantially parallel to the fuselage comprising clutch means controllable by the pilot during flight.

8. In an aircraft having a fuselage, motor means driving a horizontal propeller, a. flxed wing driven by said propeller adapted tosupport the aircraft during flight, a rotating wing mounted on the forward portion of said fuselage comand away from said fuselage.

9. In an aircraft h'avingoa fuselage extending longitudinally in the, airflow direction, motor means driving a horizontal propeller, a fixed wing on said fuselage adaptedv to support the aircraft during flight, a member adapted to be projected axially and upwardly above the fuselage, a blade carried by said member, and extending radially in a single direction from the member, means to said blade in. a rearwardly' position over-part of the fuse.-

lage. and means for moving said memberaxia'lly and downwardly to bring said blade into compact relation with thefuselagi-i. l0.- In an aircraft having a fuselage extending longitudinally in the airflow direction, means driving a horizontal propellena wins n ss dlw f bo tflie aircraft during flight. amember tobe projected axially and upwardly above the, fusea blade carried-by said member and ex.- tending radially in a single direction from the member, means to arrest said blade in a rear-' 'w'ardly directed position over part of the'fuselage, means for member axially mum biadeinto compact relation with the fuselage, means for projecting said member, and means operatively connecting the member to the motorto drive saidblade.

11. In an aircraft having a fuselageextending longitudinally in the airflow direction, motor means driving a horizontal propeller, a flxed wing on said fuselage adapted to support the aircraft during flight, a member adapted to be projected axially and upwardly above the fuselage, a blade carried by said member and extending radially in a single direction from the member, said fuselage being provided with longitudinal housin means which extends rearwardly from said member, and means for moving said shaft axially and downwardly to bring said blade into said housing means.

12. In an aircraft having a fuselage extending longitudinally in the airflow direction, motor means driving a horizontal propeller, a flxed wing on said fuselage adapted to support the aircraft during flight, a member adapted to be projected axially and upwardly above the fuselage, a blade carried by said member, and extending radially in a single direction fronf the member, said fuselage being provided with longitudinal housing means which extends rearwardly from said member, means for moving said member axially and downwardly to bring said blade into said housing means, means .for projecting said member axially and upwardly to elevate the blade out of said housing, and means for operatively connecting said member to said motor to effect driving of the blade.

13. In an aircraft having a fuselage extending longitudinally in the airflow direction, motor said member axially and downwardly to bring said blades into lasev 14. In an aircraft having a fuselage extending compact relation with the fuselongitudinally in the airflow direction, motormeans driving a horizontal propeller, a wing on said fuselage adapted to support the aircraft during flight, a member adapted to be projected axially and upwardly above the fuselage, a plurality of blades carried by the member, each adapted to extend radially outwardly in a single direction from the member,means for loeating said blades in different radial directions,

means for arresting said blades and locating them in a rearward direction with their axes parallel to the major or the. fuselage and above the fuselage meansformoving member axially and downwardly to bring said blades into compact relation with the fusfeiagameans for projecting said member ,axiallyand to elevate said blades. and means operatively connecting the member to the motor to drive said blades.

15. In an aircraft having a fuselage extendin longitudinally m the airflow direction, means driving a horiaontal propeller, a fin on said fuselage adaptedto su pport aircraft during flis t. a member t9 be W W axially and upwardly above theiusel'asc. a Pluralit! of blades carried bathe member; eachadaptedtoextendradiallyoutwai'diyinaslngle direction from the membeni'neansior locatin said blades in diflerent radial directions. said fuselage being provided withiongitudlnai housing means which extendsrearwardiy from said 'member.meansforarrestingsaidbladesandlo-- eating them in areal-ward direction with their major axesparailelto'themajoraxiaoi themselageandahovesaidhousfngmeanaand means for movingsaidmemberaxiailvanddownwardly' tobringsaidbla'desintosaidhousingmeans.

16. In-an aircraft having a fuselage extending longitudinally in the airflow direction, motor meansdrlvingahorisontaipropeiienaiixedwing on said adapted tomorttheaircraft a member adapted to be projectedaxialig and upwardly. above the fuselage. a pinthe blades.'

of blades carrledbv the member; each adapiedtoextendradiaiivoutwardlyinalinal mlioraxesparaileitothemaioraxisoithefuse-l lace and above said -housing means. means tormovingsaidmembera'xiailyanddownwardlv" to bring said blades into said housing means.

means for projecting said member axially and upwardly to elevate the biades out of said housingmeansgandmeanstoroperativelyeonnecting said member to said motor to elect driving of momma 3.8m 

